Propeller structure



P 1965 c. A. SERRIADES 3,180,424

PROPELLER STRUCTURE Filed March 25, 1963 2 Sheets-Sheet 1 INVENTOR. Canszaflzfle A. fZlQCiSe 2 BY l I g 2 TTORNEYS April 27, 1965 c. A. SERRIADES 3,180,424

PROPELLER STRUCTURE Filed March 25, 1963 2 Sheets-Sheet 2 I II HI I A ORNEYS United States Patent 3,180,424 PROPELLER STRUCTURE Constantine A. Serriades, 3959 N. Lake Shore Brive, Chicago, Ill. Filed Mar. 25, 1963, Ser. N 267,579 9 Claims. (Ci. Mil-135.4)

This invention relates to a jet propelled propeller, and more particularly to a propeller comprising a number of blade portions interconnected at the tips and having a built-in jet propulsion means for rotating the propeller.

An object of the present invention is to provide a new and improved propeller employing jet propulsion means for rotation.

A further object of the present invention is to provide a simple power plant for aircraft which can be economically constructed with a minimum of parts.

A further object of this invention is to simplify the repair and maintenance of the power plant of an aircraft.

A further object of this invention is to provide a propeller comprising a number of blade portions interconnected at their tips to provide added thrust when rotated.

A further object of this invention is to provide a unique jet engine for use at the tip of a propeller.

A further object of this invention is to provide a jetpropelled propeller of unitary construction, preferably for use with a helicopter type aircraft, but which can be used on other types of aircraft as well.

Briefly, the embodiment of the invention disclosed herein comprises a propeller made up of a number of propeller blades mounted next to each other on the propeller shaft and at a slight rotational angle to each other. Adjacent blade portions are interconnected at their tips by a relatively flat-surfaced arcuate sector. Several small jet engines, integral with the arcuate sector, are provided to rotate the propeller. By reason of the fact that the propeller portions are mounted next to each other on the shaft with an arcuate sector extending between the tips, each arcuate sector is disposed so as to extend through a plane at a slight angle to a plane normal to the propeller shaft. Each arcuate sector is, in this manner, generally parallel to the blade of each propeller portion. In this manner, each sector provides an additional lifting or thrust surface when the propeller is rotated by the jet engine. If desired, slots having end walls at a slight angle to the direction of rotation can be provided in each arcuate sector for even greater thrust.

The invention will be more fully understood from the following detailed description of an embodiment thereof.

0n the drawings:

FIGURE 1 is a plan view of a propeller having two blade portions and a flat-surfaced arcuate sector interconnecting adjacent tips of the propeller portions. Also shown is a slot in each sector for providing added thrust.

FIGURE 2 is an elevational view taken along line IIII of FIGURE 1, showing the jet engines which are disposed adjacent the tips of each of the adjacent blades. The blade hubs are shown adjacent each other on the propeller shaft.

FIGURE 3 is an enlarged cross-sectional view taken along line lIIIlI of FIGURE 1, showing a jet engine.

FlGURE 4 is a plan View of a modification of this invention, showing a larger number of blades having interconnecting sectors.

FIGURE 5 is an elevational view taken along line VV of FIGURE 4, showing the arcuate sectors spaced apart and slightly overlapping, so as to create a bi-plane effect.

FIGURE 6 is an enlarged cross-sectional view of the jet engines taken along line VlVI of FIGURE 4.

Referring now to the drawings, in FIGURES 1 and 2,

EddbAZd Fatented Apr. 2?, 1%55 "ice there is shown a propeller Ill of the instant invention for use on an aircraft (not shown) having a rotational shaft 11 extending therefrom and rotatable in the direction shown by arrows A and B. The propeller it? comprises two propeller portions 12 and 13, having hubs l4 and 15 respectively, which are mounted adjacent each other on the rotatable shaft 211. The propeller portion 12 has a blade section 16 and a blade section 17 extending from either side of the hub is, while the propeller portion 13 has a blade section 18 and a blade section 19.

An arcuate sector 2t? is shown between the tips of the blade sections 16 and 18 and is integral therewith. Similarly, an arcuate sector 43 is disposed between the tips of the blade sections 17 and 19. It should be noted that the portion of the propeller ill to the right of the shaft 11 (as viewed in FIGURE 1) is identical to the portion to the left of the shaft ll. Accordingly, only the left portion will be described hereafter.

In FIGURE 2, it is observed that the jet propulsion means 21 and 22, having enlarged body members 23 and 24 respectively integral, with or built into the sector 23', are disposed adjacent the tips of the blades 16 and 13. As seen in FIGURE 3, the body member 23 has a generally V-shaped leading contour 25, with an intake port 27 disposed below the V-shaped contour 25. An S-shaped flow path 26 is formed in the body member 23, with the direction of flow indicated by the arrows C and D. Air entering the intake port 27, positioned below the plane of the sector 26), passes a fuel nozzle 28, an igniting means 29, through a grid means 3t! which maintains combustion of the fuel-air mixture, and through an exhaust port 31 located above the plane of the sector 20 and directed tangentially to the blade 16. A trailing contour 32 of the body member 23 is acre-dynamically shaped to allow air to pass freely thereover.

Similarly, the body member 24 has an acre-dynamically shaped leading contour 33, an intake port 34, a fuel nozzle, igniting means and a grid means (all not shown) and an exhaust port 35 directed tangentially to the blade 18. Notice that a trailing contour 45 of the body member 24 is generally V-shaped, with the exhaust port 35 disposed above the V-shaped contour 45.

Fuel is fed to the fuel nozzles of the jet propulsion means 21 and 22'tl1rough hollow passages 36 and 37 respectively extending from the fuel line 38 in the center of the shaft 11. Operation of the jet propulsion means 21 and 22 creates exhaust gases which are emitted from the exhaust ports 31 and 35, tangentially to the peripheries of the blades 16 and 18 respectively. The exhaust gases thus create a thrust which rotate these blades about the shaft 11 in the direction shown by the arrows A and B. The structure of the propeller iii of the instant invention is consequently much more than the mere provision of jet propulsion means at the tips of a propeller. The blades 16 and 18 have leading edges 39 and 4t; respectively which are directed 'or tipped slightly away from the aircraft, and trailing edges 41 and 42 which are directed slightly toward the aircraft. By mounting the propeller portions 12 and 13 adjacent each other and placing them at a slight rotational angle relative to each other, the generally flat surfaces of the sectors 26 and 43 which interconnect the tips of the blades, lie in a plane which is substantially parallel to the normal planes of the blades. For this reason, the sectors 2t} and 43 act as an additional thrust surface, similar to that of the blades 16 to 19.

Driving the propeller It by jet propulsion means utilizes the additional thrust surface provided by the sectors 2.0 and 43. Even greater thrust is created by the novel construction of the integral sector 2tl and the jet propulsion means 21 and 22. For example, directing the exhaust port 31 across the upper surface 44 of the sector 2% creates an area of partial vacuum near the upper a direction parallel to the shaft 11.

j the arrow H.

I sage 92 and through the web 75.

f thrust surface.

surface 44 which causes the sector 2% to be continuously 7 viding a slot 46 having a pair of end walls 47 and 48 lying at a slight angle to the shaft 11. Air flow through the slot 46 tends to urge the sector Ztl' upwardly and in In the modification shown in FIGURES 4 to 6, a propeller SIB including a group 51 of three blades'52, 53and as (having blade sections 59 to so, 61 and s2, 63 to 64, respectively) have been provided adjacent each other on a rotatable shaft 55. A spacer 55 on the shaft 55 positions a fourth blade 57 (having blade sections 65 :and, 66) a predetermined distance below the group 51.

Once again, the portion'of the propeller to the right of the shaft 55 (as viewed in FIGURE 4) is identical to the portion to the left of the shaft 54. Therefore, only the left portion will be described hereafter.

' The direction of rotation of the propeller 5G is as indicated by arrows E and F in FIGURES 4 and 5, respectively. A first fiat arcuate sector 58 integrally connects'the tips of the blade sections 59, 61 and 63. Jet propulsion means 67, as and 69 are provided adjacent the respective tips of the aforementioned blades. A second flat arcuate sector 79 is integral with'the tip of the blade section 65 and is disposed in a plane substantially parallel to and slightly overlapping the plane of the first sector 58. Other jet propulsion means 72 and 73, integral with the second sector 70, are disposed directly below and opposite the jet propulsion means as and 68 respectively. Web members 74 and '75 interconnect the jet means 69 and 72, and 63 and '73 respectively. Notice particularly that the jet propulsion means 72 and 'l3 have no blades integral therewith, but are supported only by the. web members 74 and '75, and the second sector '79. J 7 V The detail construction and operation of each jet propulsion means is substantially as described for FIGURES l to 3. For example, see FIGURE 6 where it is shown that the jet means 68 is substantially the same width as the first sector 58, and has an aero-dynamically shaped leading contour 76 and trailing contour 77. ,Air enters an intake port 7 8 as indicated by the arrow G, and moves merits Will be readily apparent to those skilled in the through a substantially, S-shaped flow path 7) past a fuel nozzle 80, an igniting means 81, through a grid'means 82 which'maintains combustion of the fuel-air mixture, and through an exhaust port 83 and out as indicated by In like manner, the jet propulsion means 73 is substantially the same width as the jet propulsion means 63 and has a generally V-shapedleading contour n 84. And an acre-dynamically shaped trailing contour:

85. Air enters an intake port 86 as indicated by the arrow I, and moves through a substantially S-shaped flow path $7, past a fuel nozzle 88, an igniting means' 89,

through a grid means 9i}, and through an exhaust port 91 and out as indicatedby the arrow K. Fuel is fed to the'fuel'n'ozzle 8%} of the jet propulsion means 68 through ahollow passage 92 (in the blade 61 extending from a fuel line 93in the center of the'shaft 55. Similarly, fuel is fed to the fuel nozzle 88 of the jet propuls on means '73 through a duct 94 which extends from the pas- @The modified propeller so shown in FIGURESA to 6, is constructed to provide even greater thrust surface than the former structure by reason of the greater length of the sectors 58 and 7d, as Well as the bi-plane positioning 'of these sectors, The greater'thrust surface is accompanied by several additional 1 jet propulsion means w to'rotate the propeller 5%}, so as to utilize this greater art. Therefore, the invention should not be limited to the particular arrangement shown and described but should encompass all modifications within the spirit and scopeof the appended claims. a

Iclaim as my invention:

1. In a propeller structure including a rotatable propeller shaft:

(a) a plurality'of blades mounted on said shaft,

(12) an arcuate member connecting the'outer ends of at least two adjacent blades,

(c) said member having therein an S-shaped passage with an intake adjacent a leading edge, an exhaust adjacent a trailing edge, and an intermediate portion thatturns from said intake toward said leading edge,

(11) said shaft and at least one of said blades provid ing arconnecting fuel line opening into said S-shaped passage, and f (2) means in said passage for thing said fuel mixture with air introduced into said intake.

, 2'. A propeller structure for use with an aircraft having a rotatable shaft extending therefrom, said propeller structure comprising: a (a) a plurality of propeller portions mounted adjacent each other'on said shaft, and disposed at a rotational angle relative to each other,

(h) each said propeller portion having a blade on either side of said shaft,

(a) each said blade having a leading and a trailing edge,

,(d) 'a'flat arcuate sector extending between the tips of adjacent blades, and having a first surface and a second surface disposed away from said first surface,

(:2) jet propulsion means for rotating said blades about said central axis, said jet propulsion means including,

, (f), an enlarged body member integral with said sector opposite the tip of at least one of said blades, and

in adhaving a front portion corresponding to said leading edge anda rear portion'corresponding to said trailing e g r H (g) said front portion being acre-dynamically formed so as to permit uninterrupted flow of air thereacross, and including an intake port therein, said intake port disposed adjacent the plane of said first surface,

(h) said rear portion having an exhaust port therein,

a (i) a substantially S-shaped flow path through said (a) a lower propeller portion and an upper propeller portion disposed in stack relationship on said shaft, (b) each said propeller portion having a hub mounted on said shaft and having a blade extending'from either side of'said'hub, I v 7 (0) each said blade having'a leading'edge and a trailingedge,;

(d) said upper'propeller portion disposed at a rota- V ,tionalafngle to said lower propellerrportion such that each said leading edge of said upper propeller portion is slightly in advance of said leading edge. of said "lower propeller portion, I

'(e). :a pair of flat arcuate sectors, each extending betweenthe tip of one blade of said llower propeller portion ant l the tip of the adjacent blade of said upper A propeller portion," v

i (f) jet propulsion means forrotatingsaid blade about 75. I

said shaft includin'g i (g) a first pair of enlarged body members integral with each said sector and disposed opposite the tip of each blade of said upper propeller, each of said first body members of substantially the same width as said sector, and having a generally V-shaped leading contour, with an intake port disposed below said V- shaped contour and below the plane of said sector, and having an acre-dynamically shaped trailing contour with an exhaust port disposed therein, said ex- (h) an enlarged body member substantially the Width of said sector, and having an intake port disposed behind the plane of said respective sector, and having haust port positioned above the plane of said sector 10 an exhaust port disposed in front of the plane of said and di ectly t ng nti lly t0 Said blade, respective sector and directed tangentially to said 3 Second P111r 0f enlarged y members gral blades and across the front plane of said sector,

with Said Sector and dlsposfid Opposite the p of each (i) a substantially S-shaped flow path through each of blade of d lower propeller, each of said second said body members from said intake port to said body members of substantially the same width as said h t t, Sector, and having all aero-dyllamicany Shaped j) fuel means for supplying fuel to said flow path, ing contour With all intake P disposed below the (k) means positioned in said flow path for igniting plane of said sector, and having a generally V-shaped said mixture, trailing contour, with an exhaust port disposed therein (m) and mgans f i i i combustion f id and positioned above the plane of said sector and mixture directed tangentially to said blade, 7 A propeller m m i i a substanllany P flow PE1th through each of (a) a plurality of propeller portions mounted adjacent said body members from said inlet P t0 said each other on a central axis, each disposed at a P rotational angle relative to the other, (1) fuel means fo F P Y of fuel to Sald flow Path (b) at least one of said propeller portions spaced apart mFans for lgmtmg f f l and on said central axis from the remaining of said pro- (l) grid means for maintaining combustion of said peller portions,

mixture. 4. A propeller structure as claimed in claim 2 wherein: i iii s f i g gs g ggf havmg a blade on (a) each of said sectors has an arcuate slot along the (d) Said blades of Said remaining propeller portions length thereof, the end walls of which lie at a slight angle to said shaft,

disposed in a first group on one side of said central axis and a second group on the other side thereof, whereby said first group of blades and one of said blades of said one propeller portion form a stair-step arrangement in a direction parallel to said central axis,

whereby air flow through said slot tends to urge said sector in a direction parallel to said shaft and away from said helicopter.

5. A propeller structure comprising:

(a) a plurality of propeller portions mounted adjacent each other on a central axis, each disposed at a rotational angle relative to the other,

(12) at least one of said propeller portions spaced apart (e) a first pair of fiat arcuate sectors extending between the tips of said blades of said first and second groups respectively,

(1) a second pair of arcuate sectors, each extending on said central axis from the remaining of Said from the tip of one of said blades of said one propeller Demons p peller portion and disposed substantially parallel to, (0) each of said propeller portions having a blade on g gpart and slightly oYeriappmg sald each either side of said central axis, 0 Sal pan 0 sectors respeclwe (d) a first pair of fiat arcuate sectors, each extendin (g) a plurality of F members mterconnectmg Sald circumferentially from the tip of one of said blades lfirst and se-cond R of sectqrs of said one propdler portion z) a plurality of et propulsion means integral with (e) a second pair of flat arcuate sectors integral with each of sald first and.second Pan Sectors i the tips of the blades of said rernainin prope ler porhaving an exhaust i dlrected tangepnally to i tions each of Said Second pair of 2 (fisposed blades for rotating said blades about said central axis. substanfiany Parana to Spaced apart from and 8. A propeller structure for use with a helicopter havslightly overlapping each of said first pair of sectors, (1) a plurality of web members interconnecting said first and second pair of sectors, (g) a plurality of jet propulsion means integral with ing a rotatable shaft extending upwardly therefrom, said propeller structure comprising:

(a) three propeller portions mounted in stacked relationship on said shaft, each disposed at a slight rotational angle relative to the other each of said first and second car of sectors and having an exhaust port therein flirected tangentially to (b) smgle E portion mounted on Sald Shaft said blades for rotating said blades about said central predetermmed distance below Said Propeller pop axis. trons, A propeller structure comprising, (0) each of said propeller portionshaving a blade on (a) a plurality of propeller portions mounted adjacent 6o elthe? Side of Sald i each other on a central axis each disposed at a (d) saxlblades of Said three ropener. Pomons i rotational angle relative to the 'other posed in a first group on one slde of said central axis, (b) at least one of said Propeller portions spaced apart and a second group on the other side thereof, Whereon said central axis from the remaining of said proby f first group of and one of W blades 11 portions 65 of said one propeller portion form a stair-step arh f i propengr portions having a blade on rangement in a direction parallel to said central axis, either id f id t l i (e) an upper pair of fiat arcuate sectors extending be- (d) a first pair of flat arcuate sectors extending cirtween the tips of said blades of said first and second eumferentially from the tip of each blade of said groups p y,

one propeller portion,

(2) a second pair of flat arcuate sectors integral with the tips of the blades of said remaining propeller portions, each of said second pair of sectors disposed substantially parallel to, spaced apart from, and

(f) a lower pair of arcuate sectors, each extending circumferentially in the direction of rotation, from the tip of one of said blades of said single propeller portion and extending beneath the tips of two blades of said first and second groups,

7* a (g) a plurality of Web members extending downwardly from said upper pair of sectors opposite the tips of said-two blades ofJsaid first and second groups to said lower pair of sectors, whereby said upper and lower sectors are rigidly interconnected,

(h) a plurality. of jet propulsion means integral with a each of said sectors for rotating saidblades about said shaft, eachincluding (i) an enlarged body member substantially the width of said respective sector, and having an intake port disposed below the plane of said respective sector, and having an exhaust port disposed above the plane of said respective sector and directed tangentially to said blade and across the upper plane of said sector,

(j) a substantially S-fshaped flow path through each of said body members from said intake port to said exhaust port, I

- (k) fuel means for supplying fuel to said flow path,

(I) means positioned in said flow path for igniting said mixture, (m) and means for maintaining combustion of said mixture. a

i 9. A propeller structure for use with an aircraft having a rotatable shaft extending therefrom, said propeller structure comprising:

(a) a plurality of propeller portions mounted adjacent each other on said shaft, and disposed ata rotational angle relative to each other,

(b each said propeller portion having a blade on either side of said shaft,

' each said blade having a leading and a trailing edge, p V (d) a flat arcuate sector extending between the tips of adjacent blades,and having a first surface and a D g l second surface disposed away from said first surface, (e) jet propulsion means for rotating said blades about said central axis, said jet propulsion means'including, V

(f) an enlarged body member integral Withsaid sector ond surface creates an area of partial vacuum near said second surface which causes said sector to be continuously urged toward said area.

' References Qitedhy the Examiner UNITED STATES PATENTS 9/83 7 Bell et al r -172 1/92 Myers 170--171 6/20 Willour 170-165 10/33 Langdon 170-1354 5/39 Barnett 170172 5/51 Hays 170135.4 9/51 Alexandre 170-168 10/54 Kerry 170--135.4

JULIUS E. WE'ST, Primary Examiner. 

1. IN A PROPELLER STRUCTURE INCLUDING A ROTATABLE PROPELLER SHAFT; (A) A PLURALITY OF BLADES MOUNTED ON SAID SHAFT, (B) AN ARCUATE MEMBER CONNECTING THE OUTER ENDS OF AT LEAST TWO ADJACENT BLADES, (C) SAID MEMBER HAVING THEREIN AN S-SHAPED PASSAGE WITH AN INTAKE ADJACENT A LEADING EDGE, AN EXHAUST ADJACENT A TRAILING EDGE, AND AN INTERMEDIATE PORTION THAT TURNS FROM SAID INTAKE TOWARD SAID LEADING EDGE, (D) SAID SHAFT AND AT LEAST ONE OF SAID BLADES PROVIDING A CONNECTING FUEL LINE OPENING INTO SAID S-SHAPED PASSAGE, AND (E) MEANS IN SAID PASSAGE FOR FIRING SAID FUEL IN ADMIXTURE WITH AIR INTRODUCED INTO SAID INTAKE. 